CN103864451A - Preparation method of carbon fiber-reinforced ultra high-temperature ceramic-base composite material capable of being repeatedly ablated for use - Google Patents
Preparation method of carbon fiber-reinforced ultra high-temperature ceramic-base composite material capable of being repeatedly ablated for use Download PDFInfo
- Publication number
- CN103864451A CN103864451A CN201410116784.4A CN201410116784A CN103864451A CN 103864451 A CN103864451 A CN 103864451A CN 201410116784 A CN201410116784 A CN 201410116784A CN 103864451 A CN103864451 A CN 103864451A
- Authority
- CN
- China
- Prior art keywords
- composite material
- rare earth
- carbon fiber
- temperature ceramic
- ultra
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Ceramic Products (AREA)
Abstract
本发明涉及一种可重复烧蚀使用的碳纤维增强超高温陶瓷基复合材料的制备方法，采用真空压力浸渍结合反应性熔体渗透在传统碳纤维增强超高温陶瓷基复合材料中，以La、Y、Yb、Sc等稀土金属元素的加入起到减少高温下SiO2的挥发、稳定ZrO2/HfO2晶型以及生成稀土锆酸盐或稀土铪酸盐的作用。烧蚀过后，材料表面形成玻璃态SiO2填充于ZrO2/HfO2之间，并混合有稀土锆酸盐/稀土铪酸盐的致密层，对材料起到良好保护，使得超高温陶瓷基复合材料的可重复烧蚀性成为可能。
The invention relates to a method for preparing a carbon fiber reinforced ultra-high temperature ceramic matrix composite material that can be repeatedly ablated. It adopts vacuum pressure impregnation combined with reactive melt infiltration into the traditional carbon fiber reinforced ultra high temperature ceramic matrix composite material. La, Y, The addition of rare earth metal elements such as Yb and Sc can reduce the volatilization of SiO 2 at high temperature, stabilize the crystal form of ZrO 2 /HfO 2 and generate rare earth zirconates or rare earth hafnates. After ablation, the surface of the material forms a glassy SiO 2 filled between ZrO 2 /HfO 2 , and is mixed with a dense layer of rare earth zirconate/rare earth hafnate, which protects the material well and makes the ultra-high temperature ceramic matrix composite Repeatable ablation of the material becomes possible.
Description
Technical field
The present invention relates to the preparation method that a kind of carbon fiber that repeats ablation use strengthens ultra-temperature ceramic-based composite material, strengthen ultra-temperature ceramic-based composite material situ at carbon fiber and introduce the rare earth compounds such as La, Y, Yb, Sc, can develop a kind of ultra-temperature ceramic-based composite material that can repeat ablation property that has.
Background technology
Continuous Fiber Reinforced Silicon Carbide Composites (C/SiC) is a kind of desirable high-temperature structural material, there is the series of advantages such as high temperature resistant, low density, high strength, anti-thermal shock, have a wide range of applications at space industry, but when temperature exceedes 1700 DEG C, C/SiC initiatively oxidation loses surperficial SiO
2protective layer, anti-ablation and antioxidant property sharply decline and cause component failure.Superhigh temperature ceramics has the series of advantages such as high fusing point, high rigidity, hot strength, be considered to the candidate material under extreme heat chemical environment, therefore in C/SiC matrix material, add superhigh temperature ceramic material and become a kind of effective ways that improve its hot stage Burning corrosion resistance energy.ZrB
2, ZrC, HfB
2, HfC is because its good chemical stability, high thermal conductivity, relatively low density become the emphasis of research.Document " Yiguang Wang, Xiaojuan Zhu, Litong Zhang, Laifei Cheng.C/C-SiC-ZrC composites fabricated by reactive melt infiltration with Si
0.87zr
0.13alloy[J] Ceramics International38 (2012) 4337-4334 " in the C/C-SiC-ZrC matrix material that obtains there is good anti-oxidant and Burning corrosion resistance energy.The people such as Wang Yiguang, Pi Huilong adopts the standby C/SiC-ZrB of reactive melt infiltration legal system
2-ZrC matrix material has higher flexural strength, owing to forming Zr-Si-O glass and ZrO
2-SiO
2its linear ablative rate of successive layers only has 0.002mm/s.
But, under high temperature and blast air souring, ultra-temperature ceramic-based composite material SiO
2protective layer highly volatile runs off, and ZrO
2, HfO
2in the process of temperature variation, follow the transformation of crystal formation Deng oxidation products, volume change forms loose porous structure, and material surface lacks effective protective layer, makes above-mentioned materials be difficult to bear repetition ablation, and what greatly reduce material can repeating utilization factor.
Summary of the invention
The technical problem solving
For fear of the deficiencies in the prior art part, the present invention proposes a kind of preparation method of the carbon fiber enhancing ultra-temperature ceramic-based composite material that repeats ablation use, strengthen ultra-temperature ceramic-based composite material situ at carbon fiber and introduce the rare earth compounds such as La, Y, Yb, Sc, develop a kind of ultra-temperature ceramic-based composite material that can repeat ablation property that has.
Technical scheme
The carbon fiber that repeats ablation use strengthens a preparation method for ultra-temperature ceramic-based composite material, it is characterized in that step is as follows:
Step 1, prepare composite preform: adopt CVI densifying method to prepare carbon-fiber reinforced carbon C/C or carbon fibre reinforced silicon carbide C/SiC composite preform, adopt ultrasonic cleaning precast body to be no less than 30 minutes, in the baking oven of 80 DEG C～100 DEG C, dry and obtain clean dry precast body; The ventilate rate of described precast body is 20vol%～30vol%;
Step 2, prepare slurry: C organic precursor and hexamethylenetetramine are dissolved in dehydrated alcohol, then add containing rare earth metal presoma ball milling and obtain slurry; 0.1 times of the quality of the organic precursor that described hexamethylenetetramine quality is C; Described rare earth metal presoma and C organosilane precursor body mass ratio are 2:1～10:1; The viscosity of the content control slurry of described dehydrated alcohol is 50～100mPas;
Step 3, vacuum pressure impregnation: by carbon fabric perform in vacuum tightness be-0.08MPa～-0.10MPa, pressure is to be immersed in slurry under the environment of 0.8MPa～1.0MPa, and rare earth metal presoma and C organic precursor in slurry are impregnated in precast body;
Step 4, curing cracking: the material that dipping is completed is dry 4-10 hour in 80 DEG C of-100 DEG C of baking ovens are solidified 30～60 minutes in 130 DEG C～150 DEG C baking ovens, and then 2 hours cracking organic C presomas of lower 900 DEG C～1800 DEG C thermal treatments of argon shield;
Step 5, reactive melt infiltration RMI: under hot conditions and vacuum condition, superalloy is infiltrated to the material of step 4 gained and generate ultrahigh-temperature phase with C organosilane precursor precursor reactant original position, obtain repeating ablation carbon fiber and strengthen ultra-temperature ceramic-based composite material; Does is described superalloy? The temperature of described hot conditions exceeds 100 DEG C～150 DEG C than the alloy melting point of the superalloy of selecting.
In described step 2, replace rare earth compound using rare earth oxide water-based slurry and prepare slurry as presoma, method is that to add massfraction be in the sodium cellulosate CMC aqueous solution of 0.5%-1% and ball milling obtains slurry for 24 hours above by rare-earth oxide.
CVI method for densifying in described step 1 substitutes with PIP method for densifying.
The rare earth compound that described step 2 is introduced is the inorganic salt that dissolve in ethanol and the organic precursor of Yb or Sc non radioactive element in Y and La series elements or the rare-earth oxide that is insoluble to ethanol.
Described C organic precursor is resol, furane resin or silane resin.
Described superalloy is silicon, zirconium, silicon zirconium, silicon-hafnium, silicon tantalum, copper silicon, zirconium copper or the alloy that can generate with C organic precursor corresponding carbide in pyroreaction.
Beneficial effect
A kind of carbon fiber that repeats ablation use that the present invention proposes strengthens the preparation method of ultra-temperature ceramic-based composite material, adopt vacuum pressure impregnation binding reactive melt infiltration to strengthen in ultra-temperature ceramic-based composite material in traditional carbon fibres, reduce SiO under high temperature to play adding of the thuliums such as La, Y, Yb, Sc
2volatilization, stablize ZrO
2/ HfO
2the effect of crystal formation and generation rare earth zirconate or rare earth hafnates.After ablation, material surface forms vitreous state SiO
2be filled in ZrO
2/ HfO
2between, and be mixed with the tight zone of rare earth zirconate/rare earth hafnates, and material is played to good protection, make the ablative possibility that becomes that repeats of ultra-temperature ceramic-based composite material.
The invention solves SiO under existing carbon fibre reinforced silicon carbide ultra-temperature ceramic-based composite material Yin Gaowen
2the volatile flow ZrO that becomes estranged
2, HfO
2change in differing temps lower volume and cause zone of oxidation loose porous Deng oxidation products, easily avalanche, cannot carry out repeating the problem of ablation.
Brief description of the drawings
Fig. 1: C/SiC-ZrC-L
athe low multiple backscattered electron of matrix material section Photomicrograph.
Fig. 2: the high multiple backscattered electron of C/SiC-ZrC-La matrix material section Photomicrograph.
Embodiment
Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:
Embodiment 1
Composite preform preparation: adopt CVI technique, by propylene pyrolysis at 960 DEG C, at carbon fiber surface deposition PyC interphase, utilize hydrogen that MTS is written into cvd furnace, at 1000 DEG C, cracking MTS under 5KPa pressure, deposition SiC matrix, the C/SiC composite preform ultrasonic cleaning that to obtain ventilate rate be 20vol% at least 30 minutes is dried and is obtained clean dry precast body in the baking oven of 80 DEG C.
Slurry preparation: resol, hexamethylenetetramine are dissolved in dehydrated alcohol, then add La (NO
3)
3xH
2o ball milling obtain slurry for 24 hours above; Resol and nitrate ratio are 1:3, and hexamethylenetetramine quality is 0.1 times of resol quality; The viscosity of the content control slurry by dehydrated alcohol is 50～100mPas.
Vacuum pressure impregnation: C/SiC precast body and slurry are put into vacuum tank simultaneously, but do not contact with each other, vacuumize 20 minutes, make vacuum tightness be-0.08MPa～-0.10MPa, after say that precast body immerses in slurry pressurize 30 minutes, slowly air pressure is risen to 0.8MPa, pressurize is taken out for 30 minutes.
Solidify cracking: the material of preparation in step 3 is dried to 4 hours in 80 DEG C of baking ovens, in 130 DEG C～150 DEG C baking ovens, solidifies 30 minutes, and then 2 hours cracking resol of the lower 1500 DEG C of thermal treatments of argon shield.
Reactive melt infiltration RMI: under the vacuum condition of 1700 DEG C, silicon-zirconium is infiltrated to the material of step 4 gained and react original position generation ZrC, SiC with C, obtain the repeated ablation C/SiC-ZrC-La ultra-temperature ceramic-based composite material of having prepared.
Embodiment 2
Composite preform preparation: adopt CVI technique, by propylene pyrolysis at 960 DEG C, at carbon fiber surface deposition PyC interphase, utilize hydrogen that MTS is written into cvd furnace, at 1000 DEG C, cracking MTS under 5KPa pressure, deposition SiC matrix, ultrasonic cleaning at least 30 minutes for the C/SiC composite preform of the ventilate rate 20vol% obtaining is dried and is obtained clean dry precast body in the baking oven of 80 DEG C.
Slurry preparation: by La
2o
3it is in 0.5% the sodium cellulosate CMC aqueous solution and ball milling more than 24 hours that powder adds massfraction, La
2o
3massfraction is 30%, obtains slurry a; Resol, hexamethylenetetramine are dissolved in dehydrated alcohol, obtain slurry b, hexamethylenetetramine quality is 0.1 times of resol quality, and the viscosity of the content control slurry by dehydrated alcohol is 50～100mPas.
Vacuum pressure impregnation: C/SiC precast body and slurry a are put into vacuum tank simultaneously, but do not contact with each other, vacuumize 20 minutes, make vacuum tightness be-0.08MPa～-0.10MPa, after precast body is immersed in slurry a to pressurize 30 minutes, slowly air pressure is risen to 0.8MPa, pressurize is taken out for 30 minutes.After drying, same method is by the precast body vacuum pressure impregnation slurry b after drying.
Solidify cracking: the material of preparation in step 3 is dried to 4 hours in 80 DEG C of baking ovens, in 150 DEG C of baking ovens, solidifies 30 minutes, and then 2 hours cracking resol of the lower 1500 DEG C of thermal treatments of argon shield.
Reactive melt infiltration RMI: under the vacuum condition of 1800 DEG C, silicon-hafnium alloy is infiltrated to the material of step 4 gained and react original position generation HfC, SiC with C, obtain the repeated ablation C/HfC-SiC-L having prepared
aultra-temperature ceramic-based composite material.
Embodiment 3
Composite preform preparation: in carbon fabric perform, adopt pressure impregnation resol slurry, vacuum tightness is-0.08MPa, pressure is 0.8MPa, 150 DEG C solidify after at 900 DEG C cracking resin, the C/C composite preform ultrasonic cleaning that to obtain ventilate rate be 30vol% at least 30 minutes is dried and is obtained clean dry precast body in the baking oven of 80 DEG C.
Slurry preparation: furane resin, hexamethylenetetramine are dissolved in dehydrated alcohol, then add Y (NO
3)
3xH
2o ball milling obtain slurry for 24 hours above; Furane resin and nitrate ratio are 1:4, and hexamethylenetetramine quality is 0.1 times of furane resin quality; The viscosity of the content control slurry by dehydrated alcohol is 50～100mPas.
Vacuum pressure impregnation: C/C precast body and slurry are put into vacuum tank simultaneously, but do not contact with each other, vacuumize 20 minutes, make vacuum tightness be-0.08MPa～-0.10MPa, after say that precast body immerses in slurry pressurize 30 minutes, slowly air pressure is risen to 0.8MPa, pressurize is taken out for 30 minutes.
Solidify cracking: the material of preparation in step 3 is dried to 4 hours in 80 DEG C of baking ovens, in 150 DEG C of baking ovens, solidifies 30 minutes, and then 2 hours cracking furane resin of the lower 1500 DEG C of thermal treatments of argon shield.
Reactive melt infiltration RMI: under the vacuum condition of 1800 DEG C, silicon-hafnium alloy is infiltrated to the material of step 4 gained and react original position generation HfC, SiC with C, obtain the repeated ablation C/SiC-HfC-Y ultra-temperature ceramic-based composite material of having prepared.
Claims (6)
1. the carbon fiber that can repeat ablation use strengthens a preparation method for ultra-temperature ceramic-based composite material, it is characterized in that step is as follows:
Step 1, prepare composite preform: adopt CVI densifying method to prepare carbon-fiber reinforced carbon C/C or carbon fibre reinforced silicon carbide C/SiC composite preform, adopt ultrasonic cleaning precast body to be no less than 30 minutes, in the baking oven of 80 DEG C～100 DEG C, dry and obtain clean dry precast body; The ventilate rate of described precast body is 20vol%～30vol%;
Step 2, prepare slurry: C organic precursor and hexamethylenetetramine are dissolved in dehydrated alcohol, then add containing rare earth metal presoma ball milling and obtain slurry; 0.1 times of the quality of the organic precursor that described hexamethylenetetramine quality is C; Described rare earth metal presoma and C organosilane precursor body mass ratio are 2:1～10:1; The viscosity of the content control slurry of described dehydrated alcohol is 50～100mPas;
Step 3, vacuum pressure impregnation: by carbon fabric perform in vacuum tightness be-0.08MPa～-0.10MPa, pressure is to be immersed in slurry under the environment of 0.8MPa～1.0MPa, and rare earth metal presoma and C organic precursor in slurry are impregnated in precast body;
Step 4, curing cracking: the material that dipping is completed is dry 4-10 hour in 80 DEG C of-100 DEG C of baking ovens are solidified 30～60 minutes in 130 DEG C～150 DEG C baking ovens, and then 2 hours cracking organic C presomas of lower 900 DEG C～1800 DEG C thermal treatments of argon shield;
Step 5, reactive melt infiltration RMI: under hot conditions and vacuum condition, superalloy is infiltrated to the material of step 4 gained and generate ultrahigh-temperature phase with C organosilane precursor precursor reactant original position, obtain repeating ablation carbon fiber and strengthen ultra-temperature ceramic-based composite material; Does is described superalloy? The temperature of described hot conditions exceeds 100 DEG C～150 DEG C than the alloy melting point of the superalloy of selecting.
2. the carbon fiber that can repeat according to claim 1 ablation use strengthens the preparation method of ultra-temperature ceramic-based composite material, it is characterized in that: in described step 2, replace rare earth compound using rare earth oxide water-based slurry and prepare slurry as presoma, method is that to add massfraction be in the sodium cellulosate CMC aqueous solution of 0.5%-1% and ball milling obtains slurry for 24 hours above by rare-earth oxide.
3. the carbon fiber that can repeat according to claim 1 ablation use strengthens the preparation method of ultra-temperature ceramic-based composite material, it is characterized in that: the CVI method for densifying in described step 1 substitutes with PIP method for densifying.
4. can repeat according to claim 1 the carbon fiber that ablation uses and strengthen the preparation method of ultra-temperature ceramic-based composite material, it is characterized in that: the rare earth compound that described step 2 is introduced is the inorganic salt that dissolve in ethanol and the organic precursor of Yb or Sc non radioactive element in Y and La series elements or the rare-earth oxide that is insoluble to ethanol.
5. the carbon fiber that can repeat according to claim 1 ablation use strengthens the preparation method of ultra-temperature ceramic-based composite material, it is characterized in that: described C organic precursor is resol, furane resin or silane resin.
6. the carbon fiber that can repeat according to claim 1 ablation use strengthens the preparation method of ultra-temperature ceramic-based composite material, it is characterized in that: described superalloy is silicon, zirconium, silicon zirconium, silicon-hafnium, silicon tantalum, copper silicon, zirconium copper or the alloy that can generate with C organic precursor corresponding carbide in pyroreaction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410116784.4A CN103864451B (en) | 2014-03-26 | 2014-03-26 | The carbon fiber that can repeat ablation use strengthens the preparation method of ultra-temperature ceramic-based composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410116784.4A CN103864451B (en) | 2014-03-26 | 2014-03-26 | The carbon fiber that can repeat ablation use strengthens the preparation method of ultra-temperature ceramic-based composite material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103864451A true CN103864451A (en) | 2014-06-18 |
| CN103864451B CN103864451B (en) | 2016-05-25 |
Family
ID=50903535
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410116784.4A Active CN103864451B (en) | 2014-03-26 | 2014-03-26 | The carbon fiber that can repeat ablation use strengthens the preparation method of ultra-temperature ceramic-based composite material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103864451B (en) |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104909793A (en) * | 2015-05-27 | 2015-09-16 | 哈尔滨工业大学 | Ablation resistance composite material and preparation method thereof |
| CN105948821A (en) * | 2016-04-27 | 2016-09-21 | 航天材料及工艺研究所 | Lightweight carbon fiber thermal insulation material surface pore-sealing method |
| CN107278200A (en) * | 2014-12-23 | 2017-10-20 | 赛峰飞机发动机公司 | Method for manufacturing refractory components made of composite material |
| CN107445640A (en) * | 2016-10-12 | 2017-12-08 | 平顺县西沟龙鼎新材料科技有限公司 | A kind of manufacture method of C/SiC novel mechanical sealing rings |
| CN109265188A (en) * | 2018-10-10 | 2019-01-25 | 航天特种材料及工艺技术研究所 | A kind of fibre reinforced hafnium boride-tantalum boride-carbon ceramics based composites and preparation method thereof |
| CN110028330A (en) * | 2018-01-11 | 2019-07-19 | 航天特种材料及工艺技术研究所 | A kind of ceramic matric composite and preparation method thereof |
| CN111099908A (en) * | 2019-12-30 | 2020-05-05 | 浙江大学 | High-performance ceramic of carbon fiber composite rare earth lanthanum zirconate with surface coated with silicon oxide and preparation method thereof |
| CN112341234A (en) * | 2020-11-24 | 2021-02-09 | 中国科学院金属研究所 | Preparation method of low-cost and high-strength fiber-reinforced nano porous carbon composite material |
| CN112374893A (en) * | 2020-11-26 | 2021-02-19 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of high-density zirconium-based modified fine-woven puncture ceramic matrix composite product |
| CN112457020A (en) * | 2020-11-23 | 2021-03-09 | 航天特种材料及工艺技术研究所 | Multifunctional ultrahigh-temperature ceramic matrix composite and preparation method thereof |
| CN112521157A (en) * | 2020-12-24 | 2021-03-19 | 西北工业大学 | Ultrahigh-temperature ceramic matrix composite and preparation method thereof |
| CN113526972A (en) * | 2021-07-28 | 2021-10-22 | 中国科学院上海硅酸盐研究所 | A kind of rare earth modified ultra-high temperature ceramic matrix composite material with strong ablation resistance and preparation method thereof |
| CN114436680A (en) * | 2022-03-02 | 2022-05-06 | 成都理工大学 | Preparation process method of mineral material and ultrahigh-temperature ceramic synergistically modified C/C composite material |
| CN114773075A (en) * | 2022-03-10 | 2022-07-22 | 西北工业大学 | Ultra-high temperature ceramic matrix composite material with La/Y-doped ZrC-SiC coating and preparation method |
| CN115353324A (en) * | 2022-08-30 | 2022-11-18 | 航天特种材料及工艺技术研究所 | A kind of high thermal conductivity and ablation resistant composite material and preparation method thereof |
| CN116178051A (en) * | 2022-12-28 | 2023-05-30 | 中国科学院金属研究所 | Preparation method of rare earth oxide modified C/(C-) SiC-ZrC composite material |
| CN116219329A (en) * | 2023-01-04 | 2023-06-06 | 中国科学院金属研究所 | Low-cost carbon fiber reinforced metal-ceramic matrix composite for aerospace thermal protection system and preparation method thereof |
| CN116835989A (en) * | 2023-06-16 | 2023-10-03 | 中南大学 | A C/C-SiC-ZrC-ZrB2 composite material and its preparation method and application |
| CN117551947A (en) * | 2023-10-30 | 2024-02-13 | 中南大学 | Super-high temperature ceramic matrix composite material containing rare earth oxide and preparation method thereof |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102515870A (en) * | 2011-12-10 | 2012-06-27 | 西北工业大学 | A preparation method of C/SiC-ZrB2-ZrC ultra-high temperature ceramic matrix composite material |
-
2014
- 2014-03-26 CN CN201410116784.4A patent/CN103864451B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102515870A (en) * | 2011-12-10 | 2012-06-27 | 西北工业大学 | A preparation method of C/SiC-ZrB2-ZrC ultra-high temperature ceramic matrix composite material |
Non-Patent Citations (1)
| Title |
|---|
| JIA LIU ET AL.: "Polymer-derived yttrium silicate coatings on 2D C/SiC composites", 《JOURNAL OF THE EUROPEAN CERAMIC SOCIETY》, no. 33, 20 September 2012 (2012-09-20), pages 433 - 439 * |
Cited By (27)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107278200B (en) * | 2014-12-23 | 2021-02-26 | 赛峰飞机发动机公司 | Method for manufacturing refractory parts made of composite material |
| CN107278200A (en) * | 2014-12-23 | 2017-10-20 | 赛峰飞机发动机公司 | Method for manufacturing refractory components made of composite material |
| CN104909793B (en) * | 2015-05-27 | 2017-04-26 | 哈尔滨工业大学 | Ablation resistance composite material and preparation method thereof |
| CN104909793A (en) * | 2015-05-27 | 2015-09-16 | 哈尔滨工业大学 | Ablation resistance composite material and preparation method thereof |
| CN105948821A (en) * | 2016-04-27 | 2016-09-21 | 航天材料及工艺研究所 | Lightweight carbon fiber thermal insulation material surface pore-sealing method |
| CN105948821B (en) * | 2016-04-27 | 2019-05-24 | 航天材料及工艺研究所 | A kind of lightweight carbon fiber heat insulation material surface method for sealing |
| CN107445640A (en) * | 2016-10-12 | 2017-12-08 | 平顺县西沟龙鼎新材料科技有限公司 | A kind of manufacture method of C/SiC novel mechanical sealing rings |
| CN110028330A (en) * | 2018-01-11 | 2019-07-19 | 航天特种材料及工艺技术研究所 | A kind of ceramic matric composite and preparation method thereof |
| CN109265188A (en) * | 2018-10-10 | 2019-01-25 | 航天特种材料及工艺技术研究所 | A kind of fibre reinforced hafnium boride-tantalum boride-carbon ceramics based composites and preparation method thereof |
| CN111099908A (en) * | 2019-12-30 | 2020-05-05 | 浙江大学 | High-performance ceramic of carbon fiber composite rare earth lanthanum zirconate with surface coated with silicon oxide and preparation method thereof |
| CN111099908B (en) * | 2019-12-30 | 2021-04-27 | 浙江大学 | A high-performance ceramic of carbon fiber composite rare earth lanthanum zirconate coated with silicon oxide and preparation method thereof |
| CN112457020A (en) * | 2020-11-23 | 2021-03-09 | 航天特种材料及工艺技术研究所 | Multifunctional ultrahigh-temperature ceramic matrix composite and preparation method thereof |
| CN112457020B (en) * | 2020-11-23 | 2022-04-12 | 航天特种材料及工艺技术研究所 | A kind of multifunctional ultra-high temperature ceramic matrix composite material and preparation method thereof |
| CN112341234A (en) * | 2020-11-24 | 2021-02-09 | 中国科学院金属研究所 | Preparation method of low-cost and high-strength fiber-reinforced nano porous carbon composite material |
| CN112374893A (en) * | 2020-11-26 | 2021-02-19 | 西安鑫垚陶瓷复合材料有限公司 | Preparation method of high-density zirconium-based modified fine-woven puncture ceramic matrix composite product |
| CN112521157A (en) * | 2020-12-24 | 2021-03-19 | 西北工业大学 | Ultrahigh-temperature ceramic matrix composite and preparation method thereof |
| CN113526972A (en) * | 2021-07-28 | 2021-10-22 | 中国科学院上海硅酸盐研究所 | A kind of rare earth modified ultra-high temperature ceramic matrix composite material with strong ablation resistance and preparation method thereof |
| CN114436680A (en) * | 2022-03-02 | 2022-05-06 | 成都理工大学 | Preparation process method of mineral material and ultrahigh-temperature ceramic synergistically modified C/C composite material |
| CN114773075A (en) * | 2022-03-10 | 2022-07-22 | 西北工业大学 | Ultra-high temperature ceramic matrix composite material with La/Y-doped ZrC-SiC coating and preparation method |
| CN115353324A (en) * | 2022-08-30 | 2022-11-18 | 航天特种材料及工艺技术研究所 | A kind of high thermal conductivity and ablation resistant composite material and preparation method thereof |
| CN116178051A (en) * | 2022-12-28 | 2023-05-30 | 中国科学院金属研究所 | Preparation method of rare earth oxide modified C/(C-) SiC-ZrC composite material |
| CN116178051B (en) * | 2022-12-28 | 2024-06-04 | 中国科学院金属研究所 | Preparation method of rare earth oxide modified C/(C-) SiC-ZrC composite material |
| CN116219329A (en) * | 2023-01-04 | 2023-06-06 | 中国科学院金属研究所 | Low-cost carbon fiber reinforced metal-ceramic matrix composite for aerospace thermal protection system and preparation method thereof |
| CN116835989A (en) * | 2023-06-16 | 2023-10-03 | 中南大学 | A C/C-SiC-ZrC-ZrB2 composite material and its preparation method and application |
| CN116835989B (en) * | 2023-06-16 | 2024-03-22 | 中南大学 | A C/C-SiC-ZrC-ZrB2 composite material and its preparation method and application |
| CN117551947A (en) * | 2023-10-30 | 2024-02-13 | 中南大学 | Super-high temperature ceramic matrix composite material containing rare earth oxide and preparation method thereof |
| CN117551947B (en) * | 2023-10-30 | 2024-05-03 | 中南大学 | Super-high temperature ceramic matrix composite material containing rare earth oxide and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103864451B (en) | 2016-05-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103864451B (en) | The carbon fiber that can repeat ablation use strengthens the preparation method of ultra-temperature ceramic-based composite material | |
| CN103992115B (en) | A preparation method of C/SiC-HfC carbon fiber reinforced ultra-high temperature ceramic matrix composite material | |
| CN105948775B (en) | A kind of preparation method of fire-resistant oxidation resistant type lightweight carbon/carbon heat-barrier material | |
| CN102515870B (en) | A preparation method of C/SiC-ZrB2-ZrC ultra-high temperature ceramic matrix composite material | |
| CN106977217B (en) | A kind of preparation method of high-strength and high-ductility silicon carbide fiber reinforced silicon carbide ceramic matric composite | |
| JP6155439B2 (en) | Manufacturing method of parts made of CMC material | |
| CN112341235B (en) | Multiphase coupled rapid densification method for ultra-high temperature self-healing ceramic matrix composites | |
| CN103058711A (en) | Method for preparing UHTC (Ultra-High Temperature Ceramic) matrix composite material through modification of UHTC powder basal body | |
| CN104311090B (en) | A kind of hot pressed sintering/presoma cracking process prepares the method for Cf/ZrC-SiC ultrahigh temperature ceramic composite | |
| CN103265331B (en) | C/SiC/Na2SiO3 antioxidative compound coating suitable for graphite material and preparation method thereof | |
| CN103724035A (en) | Densification method for carbon fiber reinforced silicon carbonitride ceramic composite material | |
| CN106342033B (en) | Carbon fiber strengthens the preparation method of ultra-temperature ceramic-based composite material | |
| CN105399452B (en) | A kind of ceramic matric composite fast preparation method | |
| CN106699209A (en) | Preparation method of continuous alumina fiber-reinforced aluminum oxide ceramic matrix composite material | |
| CN105060913B (en) | Preparation method of C/C-SiC composite material with low thermal expansion coefficient | |
| CN109437943A (en) | A kind of Cf/C-SiC-ZrB2Composite material and preparation method | |
| CN112142486A (en) | Preparation method of ablation resistant silicon carbide fiber reinforced ceramic matrix composites | |
| CN103724042B (en) | A kind of lamination mixes the preparation method of solar heat protection sandwich | |
| CN103979974B (en) | A kind of C/SiC-HfB 2the preparation method of-HfC ultra-temperature ceramic-based composite material | |
| CN112409003B (en) | A kind of hybrid matrix silicon carbide-based composite material and preparation method thereof | |
| CN105541416B (en) | A kind of preparation method of C/C composite material surfaces HfC SiC coatings | |
| CN103964882A (en) | Preparation method for fiber-reinforced superhigh temperature ceramic matrix composite | |
| CN107759251B (en) | A kind of preparation method of high toughness ceramic coating on porous ceramic surface | |
| CN110668839A (en) | Low-cost high-strength carbon fiber reinforced silicon carbide composite material and preparation method thereof | |
| CN109020628A (en) | A kind of SiC nanowire enhancing porous ceramic composite and preparation method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |